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EP0080404A1 - Assembly of two joined rotationally symmetrical objects made of materials with differing co-efficients of dilatation - Google Patents

Assembly of two joined rotationally symmetrical objects made of materials with differing co-efficients of dilatation Download PDF

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Publication number
EP0080404A1
EP0080404A1 EP82402091A EP82402091A EP0080404A1 EP 0080404 A1 EP0080404 A1 EP 0080404A1 EP 82402091 A EP82402091 A EP 82402091A EP 82402091 A EP82402091 A EP 82402091A EP 0080404 A1 EP0080404 A1 EP 0080404A1
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EP
European Patent Office
Prior art keywords
casing
cover
materials
parts
links
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP82402091A
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German (de)
French (fr)
Other versions
EP0080404B1 (en
Inventor
Marcel Robert Soligny
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication of EP0080404A1 publication Critical patent/EP0080404A1/en
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Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/33—Arrangement of components symmetrical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/35—Arrangement of components rotated
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/32—Articulated members
    • Y10T403/32254—Lockable at fixed position
    • Y10T403/32262—At selected angle
    • Y10T403/32271—Movable brace between members

Definitions

  • the invention relates to a device for fixing two parts of revolution made of materials with different coefficients of expansion, and more particularly of an inner ejection hood on the exhaust casing of a turbojet engine.
  • French Patent 2,408,037 describes the connection of an adjustable woven carbon nozzle to an ejection structure.
  • the nozzle is surrounded by rings of refractory cement.
  • One of the rings is fixed to the structure by flexible stops and the other to the orientation cylinders by means of a metal box.
  • the fact that the nozzle is connected by movable and deformable members to the ejection channel, allows free axial as well as radial expansion of the latter, without thereby subjecting the woven carbon part to unacceptable stresses.
  • the fixing device allows the leaktight connection of two pieces of revolution with different expansion coefficients, each piece being able to freely expand both in the axial and radial directions, without their relative position being modified.
  • Figure 1 shows a partial section of ejection hood and exhaust casing connected by a fixing device according to the invention.
  • Figure 2 is a view along II of Figure 1 of a portion of the fixing device.
  • Figure 1 shows, in half-section, the exhaust casing 1 on which is fixed the internal ejection cover 2. These two parts are of revolution around the axis of the reactor.
  • said cover is made of a composite material, for example carbon / carbon or ceramic and is connected to the casing which is conventionally made of a temperature-resistant stainless metal.
  • the cover has internal ribs 3 and carries a coaxial opening 4 at its top into which opens the channel 5 for evacuating the air for internal ventilation of the shaft line.
  • the outer peripheral edge 6 of the cover has a cylindrical bearing surface 7 cooperating with a similar bearing surface 8 provided on the inner peripheral edge of the exhaust casing 1.
  • the cover is connected by three links 9, the ends 10, 11, 12 of each of which are articulated on axes maintained respectively by fastening elements 23, 15, 16 on the cover and the casing.
  • the link 9 is in the form of an isosceles triangle and has on its base, close to the casing l, a concave edge allowing good clearance of the eyes 13, 14 located in parallel planes and perpendicular to the plane of the link.
  • These eyes are articulated to the yokes 15, 16 fixed to the casing 1 by axes 17, 18.
  • the top of the link is truncated and bears in planes, parallel to those of the eyes, 13, 14, of the eyes 19, 20 movable around pivots 21, 22 held in a fixing piece 23 fixed inside the cover 2 by a bolt 24 passing through it.
  • the head of the bolt and the fixing part are separated from the poroi dividing compression forces.
  • the triangular link is a molded part formed by two lateral beams 25, 26 braced by a transverse beam 27 and a partition 28.
  • the links are preferably three in number and arranged at 120 ° on the periphery of the housing and the cover and allow the radial thermal expansion of the housing while ensuring good concentricity of the cover relative to the housing.
  • a sealing device 29 is provided, consisting of a ring of elastic strips fixed inside the exhaust casing and pressing against the inside edge of the ejection cover.
  • the device according to the invention allows, in the described embodiment, the fixing of a carbon / carbon composite ejection hood having a coefficient of expansion of the order of 6 x 10 -6 on a casing metal exhaust with expansion coefficient of the order of 16.5 x 10 -6 . the assembly being subjected to temperatures of the order of 900 ° C.
  • the device described can be used for fixing between them from all parts of revolution, having different coefficients of thermal expansion, and for which it is desired to avoid the stresses due to expansion.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
  • Exhaust Silencers (AREA)
  • Sealing Devices (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gasket Seals (AREA)

Abstract

Dispositif de fixation d'un capot en matériau composite au carter d'échappement, constitué de trois biellettes (9) disposées entre le carter et le capot. Les biellettes triangulaires portent à leurs extrémités des yeux (13, 14, 19, 20) coopérant, d'une part, avec des chapes (15, 16) fixées sur le carter (1) par l'intermédiaire d'axes (17, 18) et d'autre part, avec le capot (2) par une pièce de fixation (23) et des pivots (21, 22). La pièce de fixation est solidarisée avec le capot par un boulon (24). Le carter et le capot présentent dans leurs parties voisines coaxiales des portées coopérantes (7, 8) ainsi qu'un dispositif d'étanchéité (29).Device for fixing a cover of composite material to the exhaust casing, consisting of three links (9) arranged between the casing and the hood. The triangular links carry at their ends eyes (13, 14, 19, 20) cooperating, on the one hand, with yokes (15, 16) fixed on the casing (1) by means of axes (17, 18) and on the other hand, with the cover (2) by a fixing piece (23) and pivots (21, 22). The fixing piece is secured to the cover by a bolt (24). The casing and the cover have in their adjacent coaxial parts cooperating surfaces (7, 8) as well as a sealing device (29).

Description

L'invention concerne un dispositif de fixation de deux pièces de révolution en des matériaux à coefficients de dilatation différents, et plus particulièrement d'un capot intérieur d'éjection sur le carter d'échappement d'un turboréacteur.The invention relates to a device for fixing two parts of revolution made of materials with different coefficients of expansion, and more particularly of an inner ejection hood on the exhaust casing of a turbojet engine.

La tendance actuelle, dans l'industrie aéronautique, consiste à alléger au maximum les cellules et les moteurs en utilisant des matériaux composites de faible densité. La diminution de poids entraîne une diminution de la consommation de carburant et une augmentation de la charge transportée. Les avions d'armes font largement appel à ces matériaux, en particulier pour des éléments de voilure et de cellule. Par contre, leur utilisation dans les moteurs a été peu étendue, par suite des difficultés d'association avec les matériaux classiques à coefficient de dilatation relativement élevé.The current trend in the aeronautical industry is to lighten cells and engines as much as possible by using low density composite materials. The reduction in weight results in a reduction in fuel consumption and an increase in the load transported. Arms planes make extensive use of these materials, particularly for wing and airframe components. On the other hand, their use in motors has been limited, owing to the difficulties of association with conventional materials with relatively high coefficient of expansion.

Le brevet français 2 408 037, par exemple, décrit la liaison d'une tuyère orientable en carbone tissé à une structure d'éjection. La tuyère est ceinturée par des anneaux en ciment réfractaire. L'un des anneaux est fixé à la structure par des butées souples et, l'autre, aux vérins d'orientation par l'intermédiaire d'un caisson métallique. Le fait que la tuyère soit reliée par des organes mobiles et déformables au canal d'éjection, permet la libre dilatation axiale aussi bien que radiale de ce dernier, sans pour cela soumettre la pièce en carbone tissé à des contraintes inacceptables.French Patent 2,408,037, for example, describes the connection of an adjustable woven carbon nozzle to an ejection structure. The nozzle is surrounded by rings of refractory cement. One of the rings is fixed to the structure by flexible stops and the other to the orientation cylinders by means of a metal box. The fact that the nozzle is connected by movable and deformable members to the ejection channel, allows free axial as well as radial expansion of the latter, without thereby subjecting the woven carbon part to unacceptable stresses.

On a essayé de remplacer d'autres éléments du moteur par des pièces en materiau composite et, en particulier, le cône ou le capot d'éjection interne qui prolonge le carter d'échappement. Des essais ont montré qu'il n'était pas possible de relier le capot au carter métallique par des dispositifs connus, par exemple du brevet français numéro 1 458 204, pour fixer une chemise de protection thermique dans une chambre de post-combustion. Le système à vis et glissière utilisé permet bien la dilatation axiale, mais n'accepte que très peu la dilatation radiale. Ce dispositif n'est utilisable que pour des matériaux métalliques ayant des allongements notables.We tried to replace other parts of the engine with parts made of composite material and, in particular, the cone or the internal ejection hood which extends the exhaust casing. Tests have shown that it was not possible to connect the cover to the metal casing by known devices, for example from French patent number 1 458 204, for fixing a thermal protection jacket in an after-combustion chamber. The screw and slide system used allows axial expansion, but accepts very little radial expansion. This device can only be used for metallic materials having significant elongations.

Le dispositif de fixation, selon l'invention, permet la liaison de manière étanche de deux pièces de révolution à coefficients de dilatation différents, chaque pièce pouvant librement se dilater tant dans le sens axial que radial, sans que leur position relative soit modifiée.The fixing device, according to the invention, allows the leaktight connection of two pieces of revolution with different expansion coefficients, each piece being able to freely expand both in the axial and radial directions, without their relative position being modified.

Les explications et les figures données ci-après à titre d'exemple, permettront de comprendre comment l'invention peut être réalisée.The explanations and the figures given below by way of example will make it possible to understand how the invention can be implemented.

La figure 1 montre une coupe partielle de capot d'éjection et de carter d'échappement reliés par un dispositif de fixation conforme à l'invention.Figure 1 shows a partial section of ejection hood and exhaust casing connected by a fixing device according to the invention.

La figure 2 est une vue selon II de la figure 1 d'une partie du dispositif de fixation.Figure 2 is a view along II of Figure 1 of a portion of the fixing device.

La figure 1 représente, en demi-coupe, le carter d'échappement 1 sur lequel est fixé le capot d'éjection intérieur 2. Ces deux pièces sont de révolution autour de l'axe du réacteur.Figure 1 shows, in half-section, the exhaust casing 1 on which is fixed the internal ejection cover 2. These two parts are of revolution around the axis of the reactor.

Selon l'invention, ledit capot est en un matériau composite, par exemple carbone/carbone ou céramique et est relié au carter qui est classiquement en un métal inoxydable résistant à la température. Selon l'exemple de réalisation représenté, le capot présente des nervures internes 3 et porte une ouverture coaxiale 4 à son sommet dans laquelle débouche le canal 5 d'évacuation de l'air de ventilation interne de la ligne d'arbre.According to the invention, said cover is made of a composite material, for example carbon / carbon or ceramic and is connected to the casing which is conventionally made of a temperature-resistant stainless metal. According to the embodiment shown, the cover has internal ribs 3 and carries a coaxial opening 4 at its top into which opens the channel 5 for evacuating the air for internal ventilation of the shaft line.

Le bord périphérique extérieur 6 du capot comporte une portée cylindrique 7 coopérant avec une portée semblable 8 prévue sur le bord périphérique intérieur du carter d'échappement 1.The outer peripheral edge 6 of the cover has a cylindrical bearing surface 7 cooperating with a similar bearing surface 8 provided on the inner peripheral edge of the exhaust casing 1.

Ces portées constituent un élément du dispositif de fixation selon l'invention et permettent la dilatation axiale du carter indépendamment de celle du capot.These ranges constitute an element of the fixing device according to the invention and allow the axial expansion of the casing independently of that of the cover.

Le capot est relié par trois biellettes 9 dont les extrémités 10, 11, 12 de chacune s'articulent sur des axes maintenus respectivement par des éléments de fixation 23, 15, 16 sur le capot et le carter.The cover is connected by three links 9, the ends 10, 11, 12 of each of which are articulated on axes maintained respectively by fastening elements 23, 15, 16 on the cover and the casing.

Selon une forme de réalisation représentée figure 2, la biellette 9 est en forme de triangle isocèle et présente sur sa base, voisine du carter l, un bord concave permettant un bon dégagement des yeux 13, 14 situés dans des plans parallèles et perpendiculairement au plan de la biellette. Ces yeux sont articulés aux chapes 15, 16 fixées au carter 1 par des axes 17, 18. Le sommet de la biellette est tronqué et porte dans des plans, parallèles à ceux des yeux, 13, 14, des yeux 19, 20 mobiles autour des pivots 21, 22 maintenus dans une pièce de fixation 23 fixée à l'intérieur du capot 2 par un boulon 24 le traversant. La tête du boulon et la pièce de fixation sont séparées de la poroi

Figure imgb0001
répartissant les efforts de compression.According to an embodiment shown in Figure 2, the link 9 is in the form of an isosceles triangle and has on its base, close to the casing l, a concave edge allowing good clearance of the eyes 13, 14 located in parallel planes and perpendicular to the plane of the link. These eyes are articulated to the yokes 15, 16 fixed to the casing 1 by axes 17, 18. The top of the link is truncated and bears in planes, parallel to those of the eyes, 13, 14, of the eyes 19, 20 movable around pivots 21, 22 held in a fixing piece 23 fixed inside the cover 2 by a bolt 24 passing through it. The head of the bolt and the fixing part are separated from the poroi
Figure imgb0001
dividing compression forces.

Salon l'exemple de réalisation figurée, la biellette triangulaire est une pièce moulée formée de deux poutres latérales 25, 26 entretoisées par une poutre transversale 27 et une cloison 28.In the illustrated embodiment, the triangular link is a molded part formed by two lateral beams 25, 26 braced by a transverse beam 27 and a partition 28.

Les biellettes sont préférentiellement au nombre de trois et disposées à 120° sur la périphérie du carter et du capot et permettent la dilatation thermique radiale du carter tout en assurant une bonne concentricité du capot par rapport au carter. Bien entendu, on ne sortirait pas du cadre de la présente invention en employant un nombre de biellettes analogues supérieur à trois, les biellettes étant régulièrement réparties sur la périphérie du carter.The links are preferably three in number and arranged at 120 ° on the periphery of the housing and the cover and allow the radial thermal expansion of the housing while ensuring good concentricity of the cover relative to the housing. Of course, it would not go beyond the scope of the present invention to employ a number of similar rods greater than three, the rods being regularly distributed over the periphery of the casing.

Par suite des dilatations différentes du carter et du capot, l'étanchéité entre les portées 7 et 8 est peu ou pas assurée. Afin d'éviter que les gaz de combustion ne pénètrent dans le capot, il est prévu un dispositif d'étanchéité 29 constitué d'une couronne de lamelles élastiques fixée à l'intérieur du carter d'échappement et venant appuyer contre le bord intérieur du capot d'éjection.As a result of the different expansions of the casing and the cover, the seal between the surfaces 7 and 8 is little or not guaranteed. In order to prevent the combustion gases from entering the hood, a sealing device 29 is provided, consisting of a ring of elastic strips fixed inside the exhaust casing and pressing against the inside edge of the ejection cover.

Le dispositif, selon l'invention, permet dans l'exemple de réalisation décrit, la fixation d'un capot d'éjection en composite de carbone/carbone ayant un coefficient de dilatation de l'ordre de 6 x 10-6 sur un carter d'échappement métallique de coefficient de dilatation de l'ordre de 16,5 x 10-6. l'ensemble étant soumis à des températures de l'ordre de 900°C.The device according to the invention allows, in the described embodiment, the fixing of a carbon / carbon composite ejection hood having a coefficient of expansion of the order of 6 x 10 -6 on a casing metal exhaust with expansion coefficient of the order of 16.5 x 10 -6 . the assembly being subjected to temperatures of the order of 900 ° C.

Le dispositif décrit peut être utilisé pour la fixation entre elles de toutes pièces de révolution, ayant des coefficients de dilatation thermique différents, et pour lesquelles on désire éviter les contraintes dues à la dilatation.The device described can be used for fixing between them from all parts of revolution, having different coefficients of thermal expansion, and for which it is desired to avoid the stresses due to expansion.

La position des différents éléments constituant tout ou partie du dispositif de fixation, peut être modifiée et/ou inversée sans sortir du cadre de l'invention.The position of the various elements constituting all or part of the fixing device can be modified and / or reversed without departing from the scope of the invention.

Claims (7)

1. Dispositif de fixation de deux pièces de révolution en matériaux ayant des coefficients de dilatation différents et, en particulier, d'un capot intérieur d'éjection en matériau composite sur un carter d'échappement métallique d'un turboréacteur, caractérisé en ce qu'il comporte au moins trois biellettes (9) dont les extrémités de chacune (11, 12, 10) s'articulent sur des axes (17, 18, 21 - 22) maintenus par des éléments de fixation (15, 16, 23) sur le capot (2) et le carter (1) et en ce que les parties adjacentes coaxiales du capot et du carter comportent des portées cylindriques (7, 8} respectivement extérieure (7) et intérieure (8), coopérantes.1. Device for fixing two parts of revolution made of materials having different coefficients of expansion and, in particular, of an inner cover for ejection of composite material on a metal exhaust casing of a turbojet, characterized in that '' it comprises at least three links (9) the ends of each (11, 12, 10) of which are articulated on axes (17, 18, 21 - 22) held by fastening elements (15, 16, 23) on the cover (2) and the casing (1) and in that the adjacent coaxial parts of the cover and the casing have cylindrical (7, 8} respectively outer (7) and inner (8) co-operating surfaces. 2. Dispositif selon la revendication 1, caractérisé en ce que les biellettes sont en forme de triangle isocèle tronqué dont les sommets portant des yeux (13, 14, 19, 20) sont disposés dans des plans parallèles entre eux et perpendiculairement au plan de la biellette.2. Device according to claim 1, characterized in that the links are in the form of a truncated isosceles triangle, the vertices of which bear eyes (13, 14, 19, 20) are arranged in planes parallel to each other and perpendicular to the plane of the link. 3. Dispositif selon la revendication 1 ou 2, caractérisé en ce qu'au moins une partie des éléments de fixation sont des chapes (15, 16).3. Device according to claim 1 or 2, characterized in that at least a part of the fastening elements are yokes (15, 16). 4. Dispositif selon l'une des revendications 1 à 3, caractérisé en ce qu'au moins une partie des éléments de fixation est constituée par une pièce de fixation (23) susceptible de recevoir deux pivots (21, 22).4. Device according to one of claims 1 to 3, characterized in that at least part of the fastening elements is constituted by a fastening part (23) capable of receiving two pivots (21, 22). 5. Dispositif selon l'une des revendications 2 à 4, caractérisé en ce que la biellette est une pièce formée de deux poutres latérales (25, 26) entretoisées par une poutre transversale (27) et une cloison (28).5. Device according to one of claims 2 to 4, characterized in that the link is a part formed by two lateral beams (25, 26) braced by a transverse beam (27) and a partition (28). 6. Dispositif selon l'une des revendications 1 à 5, caractérisé en ce qu'il comporte un dispositif d'étanchéité (29) fixé sur l'une des pièces de révolution et assurant l'étanchéité avec l'autre pièce.6. Device according to one of claims 1 to 5, characterized in that it comprises a sealing device (29) fixed to one of the parts of revolution and ensuring sealing with the other part. 7. Dispositif selon la revendication 6, caractérisé en ce que le dispositif d'étanchéité est formé par une couronne de lamelles élastiques.7. Device according to claim 6, characterized in that the sealing device is formed by a ring of elastic strips.
EP82402091A 1981-11-19 1982-11-17 Assembly of two joined rotationally symmetrical objects made of materials with differing co-efficients of dilatation Expired EP0080404B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8121649A FR2516609A1 (en) 1981-11-19 1981-11-19 DEVICE FOR FIXING TWO PARTS OF REVOLUTION IN MATERIALS HAVING DIFFERENT EXPANSION COEFFICIENTS
FR8121649 1981-11-19

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Publication Number Publication Date
EP0080404A1 true EP0080404A1 (en) 1983-06-01
EP0080404B1 EP0080404B1 (en) 1985-10-23

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EP (1) EP0080404B1 (en)
JP (1) JPS58143152A (en)
DE (1) DE3267055D1 (en)
FR (1) FR2516609A1 (en)

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WO2006059977A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and corresponding orepating method
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US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
WO2006059989A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
WO2006062497A1 (en) 2004-12-04 2006-06-15 United Technologies Corporation Tip turbine engine mount
US7584621B2 (en) * 2005-08-05 2009-09-08 Siemens Energy, Inc. Radially expanding turbine engine exhaust cylinder interface
FR2903382B1 (en) * 2006-07-10 2008-10-10 Airbus France Sas DEVICE FOR HITCHING AN AIRCRAFT ENGINE COMPRISING TWO PIVOT RETRACTORS WITH EMBOITEMENT TRANSVERSE
RU2328613C1 (en) * 2006-09-18 2008-07-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Device to joint turbojet engine hinged jet nozzle with the airplane engine nacelle
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US9188024B2 (en) 2013-02-22 2015-11-17 Pratt & Whitney Canada Corp. Exhaust section for bypass gas turbine engines
US10385784B2 (en) * 2016-03-11 2019-08-20 Hamilton Sundstrand Corporation Clevis link for toggle mechanism of ram air turbine actuator
US10570780B2 (en) * 2017-11-03 2020-02-25 Rohr, Inc. Exhaust assembly mounting configuration
FR3084916B1 (en) * 2018-08-10 2020-07-17 Safran Ceramics FLEXIBLE FIXING EJECTION CONE
FR3113094B1 (en) * 2020-07-31 2022-10-14 Safran Ceram Connecting device comprising a sliding pivot type connection for connecting an exhaust casing and an exhaust gas ejection cone of an aircraft turbojet engine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB587512A (en) * 1942-05-13 1947-04-29 Frank Whittle Improvements relating to exhaust systems of jet propulsion installations in aircraft
FR1217638A (en) * 1957-11-22 1960-05-04 Snecma Improvements to reactor nozzles
GB882186A (en) * 1959-05-13 1961-11-15 Rolls Royce Improvements in or relating to joints
FR1313324A (en) * 1961-11-17 1962-12-28 Westinghouse Electric Corp Gas turbine hearth support
FR1458204A (en) * 1965-06-11 1966-03-04 Snecma Improvements to fixing devices for the thermal protection jacket of a reactor post-combustion chamber
FR1545781A (en) * 1967-09-25 1968-11-15 Snecma Improvements to the coaxial fixing devices of a central body inside a hollow body
FR1551357A (en) * 1967-12-28 1968-12-27
GB1503394A (en) * 1976-07-01 1978-03-08 Rolls Royce Metal ceramic structure
GB2007773A (en) * 1977-11-07 1979-05-23 Aerospatiale Jet propulsion nozzle

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2564042A (en) * 1946-02-27 1951-08-14 Power Jets Res & Dev Ltd Turbo-jet engine with axially expansible exhaust duct controlling area of exhaust bypass gap
US2620157A (en) * 1947-05-06 1952-12-02 Rolls Royce Gas-turbine engine
US2799472A (en) * 1953-07-03 1957-07-16 Armstrong Siddeley Motors Ltd Exhaust cone assemblies of gas turbine engines
FR1219542A (en) * 1959-03-28 1960-05-18 Nord Aviat Device for fixing and adjusting the internal ring of a combined turbojet-ramjet thruster
US3844115A (en) * 1973-02-14 1974-10-29 Gen Electric Load distributing thrust mount

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB587512A (en) * 1942-05-13 1947-04-29 Frank Whittle Improvements relating to exhaust systems of jet propulsion installations in aircraft
FR1217638A (en) * 1957-11-22 1960-05-04 Snecma Improvements to reactor nozzles
GB882186A (en) * 1959-05-13 1961-11-15 Rolls Royce Improvements in or relating to joints
FR1313324A (en) * 1961-11-17 1962-12-28 Westinghouse Electric Corp Gas turbine hearth support
FR1458204A (en) * 1965-06-11 1966-03-04 Snecma Improvements to fixing devices for the thermal protection jacket of a reactor post-combustion chamber
FR1545781A (en) * 1967-09-25 1968-11-15 Snecma Improvements to the coaxial fixing devices of a central body inside a hollow body
FR1551357A (en) * 1967-12-28 1968-12-27
GB1503394A (en) * 1976-07-01 1978-03-08 Rolls Royce Metal ceramic structure
GB2007773A (en) * 1977-11-07 1979-05-23 Aerospatiale Jet propulsion nozzle

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0316233A1 (en) * 1987-11-12 1989-05-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Assembly method for two parts having different thermal expansion coefficients
FR2623249A1 (en) * 1987-11-12 1989-05-19 Snecma ASSEMBLY CONSISTING OF TWO PIECES OF MATERIALS HAVING DIFFERENT EXPANSION COEFFICIENTS, CONNECTED THEREBY AND METHOD OF ASSEMBLY
US4907743A (en) * 1987-11-12 1990-03-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Assembly of two bodies having distinctly different coefficients of expansion
EP0513959A1 (en) * 1991-05-13 1992-11-19 General Electric Company Shear wire flange joint
US5219190A (en) * 1991-05-13 1993-06-15 General Electric Company Shear wire flange joint for a gas turbine engine
WO2007147193A1 (en) * 2006-06-23 2007-12-27 Facc Ag Guiding carrier for jet engine linings
FR2902838A1 (en) * 2006-06-26 2007-12-28 Snecma Sa EXHAUST CONE FOR THE PIPING OF A GAS VEIN AT THE END OF A TURBINE
EP1873385A3 (en) * 2006-06-26 2008-01-09 Snecma Exhaust cone for channeling a gas stream downstream of a turbine
US7866162B2 (en) 2006-06-26 2011-01-11 Snecma Exhaust cone for channeling a stream of gas downstream from a turbine
US10731567B2 (en) 2016-12-16 2020-08-04 Rolls-Royce Plc Mount structure for an aircraft ancillary engine unit

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US4452038A (en) 1984-06-05
DE3267055D1 (en) 1985-11-28
JPS58143152A (en) 1983-08-25
FR2516609A1 (en) 1983-05-20
JPH0236782B2 (en) 1990-08-20
FR2516609B1 (en) 1983-12-23
EP0080404B1 (en) 1985-10-23

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